Catapult for launching model airplanes



Sept. 23, 1952 1N. p. ASH'WOOD 1,

' CATAPULT FOR LAUNCHING MODEL AIRPLANES Filed July 29, 1949 6SheetS-Sheetl Norman D. Ashwoob ATTORNEY.

6 sheet s -shee t 3 P 0 f n e y m mm .m Q N ma w mw N. D ASHWOOD,

Sept; 23, 1952 UCATAPULT FOR LAJUNCHING-MODELAIRPLANES Filed July 29',1949' Sept. 23, 1952 N, D. ASHWOOD 2,611,355

CATAPULT FOR LAUNCHING MODEL AIRPLANES Filed July 29, 1949 QSheetS-Sheet4 INVENTOR. Norman D. As/m ood A tic/"neg 7 Sept. 23, 1952 N. D. ASHWOODCATAPULT FORLAUNC'HING MODEL AIRPLANES Filed Jill 29, 1949 5Sheets-Sheet 6 ATTORNEY fiatentec'l Sept. 23,

' Norman 1). Ashwood, Victoria, British Columbia,

Canad Application July 29, 1949, Serial No. 107,398

This invention relates to a catapult for launching model airplanes andthe like, and it .consists in the construction, arrangements andcombinations herein described and claimed.

It is an object of the invention to provide a sturdy structure forsupport of runways upon which a plane may traverse during a take-off,the structure including a projecting means for imparting the initialmovement of the plane along the runways, as well as means for releasingthe plane from the projecting means in order that the plane may assumeits flight.

It is also an object of the invention to provide a catapult device formodel airplanes wherein a carriage for support of an airplane isarranged medially and longitudinally between a pair of runways, thecarriage being spring actuated to move the plane along the runways,there being trigger means for holding the carriage in retracted positionagainst the tension of the springwith a plane in position thereon, thesupporting structure, runways and carriage guide being broken away;

Figure 2 is a front elevational view thereof;

Figure 3 is an enlarged longitudinal sectional view of the catapultwiththe plane supporting carriage in retracted position;

Figure 4 is a similar view illustrating the position of the parts at thetime of release of the plane from the carriage; V

Figure 5 is a plan view of the plane supporting carriage: W I

Figure 6 is a longitudinal sectional view taken on the line 6- 6 ofFigure 5;

Figure 7 is a sectional view taken on the line 'I-'-1 of Figure 6; t

Figure 8 is a rear elevational view of the drum for retracting the planesupporting carriage;

Figure 9 is a sectional view taken onthe line 9+9 or Figure 8;

FigurelO is afrag n ientary perspective view of 2 Claims. (Cl. 124-26)ards.

2 a portion of the supporting structure of the catapult and plane;

Figure 11 is a fragmentary top plan view of a modified form of runway;

Figure 12 is a side elevation of the supporting structure for therunway, illustrating the manner in which the upright supports may beadjusted with respect to the vertical; and I Figure 13 is a sideelevational View of the catapult as embodied in a gun style support.

, Reference is now invited to Figures 1, 2 and 12 of the drawings,wherein the supporting structure for the catapult is shown and thisembodies a pair of spaced parallel vertically disposed standards l0arranged at the front and rear of the structure. Each standard H) has ananchorage means II on the lower end thereof for engaging the ground forsupport of the stand- A plurality of braces 12 extended between thestandards afford rigidity and maintain the standards in proper spacedrelation.

The standards ill at front and rear are of identical construction, andas best seen in Figure 2, the upper end of the standards l0 has fixedthereon a T-fitting I3 for mounting a horizontal bar I4. The fitting I3is swingably mounted on the bar id but is maintained against slidingmovements by means of adjustable collars IS. The bar I4 extends beyondthe fittings 13 a distance as at [6 and has suitable elbows I"! and pipesections l8 for support of a second bar l9 immediately above the bar M.A longitudinally extended brace rod 20 is connected to respective rods14 of the front and rear support structures, at each side, and a similarrod 2| is connected between the rods [9.

As best seen in Figures 1 and 10 of the drawings, the rods 20 areconnected by transverse rods 22 and the rods 2| are connected bytransverse rods 23 for bracing the structure, as well as to afiordsupport for runways and other structure of the catapult, as will bedescribed.

Upon the rod H! a pair of T-fittings 24 are adjustably mounted, whichmay be secured in a desired position by means of set screws 25. Thefittings 24 have a vertical collar 26 within which'a hollow rod 21 issecured, slidably re-- mounted, these rails being positioned atrespective sides of the supporting structure, and function to supportrespective wings 32 of a plane 33. As will be apparent the rails 3| maybe raised and lowered to accommodate the position of wings of varioussizes and constructions of planes.

Intermediately of the bar I4 a sleeve 34 is secured and a similar sleeve35 is mounted upon the rod I9, these sleeves being connected by struts36 (see Figure 2). Upon the upper side of the sleeve 35 a U-shaped frame31 is fixed, upwardly extended legs 38 receiving a body member 39therewithin, the body being secured within the frame by suitablefastening means 40. The frame 31 extends from the front to the rear ofthe supporting structure and the body 39 is of a corresponding length.The body 39 projects above the frame 31 for mounting a catapult 4|. Thebody 39 is formed with an arcuate recess 4| extending the length of thebody and receives a cylindrical barrel member 42 therein which is of acorresponding length. The barrel member is firmly secured in the recessby suitable brackets 43 and 44 at'the rear and by a similar bracket 45at the front of the body, 'Ad-' ditional brackets may be employedifrfound necessary.

The barrel member 42 is provided with a pair of opposed slots 46extending longitudinally thereof terminating inwardly of the ends of thebarrel as indicated at 41. Slidable within the barrel member 42 there isa cylindrical plunger 48 which has a pair of pins 49 projecting fromrespective sides, these pins being received in the opposed slots 48 ofthe barrel for guidance of the plunger during movements along thebarrel. The forward end of the barrel is closed by a plug 50 andrearwardly of the plug there is a coiled spring and a cushion disk 52'for absorbing the impact of the forwardly moving plunger 48.

For causing forward movement of the plunger 48, a large coil spring 53is connected atone end to the rear end of the plunger and the other endof the spring is connected to a closure plug 54' threadedly engaged inthe rear end of-the barrel. In the operative position, as shown'inFigure 3, the coiled spring 53 is under compression; the' plunger 48being held in retracted position, by a trigger mechanism 55 which whenreleased {permits the spring 53 to force the plunger longitudinallyalong the barrel.

The body member 39 is cut away as at 56 for mounting of the triggermechanism 55. The trigger is pivoted upon a pin 51 and has a finger 58at its forward end which projects through a slot 59 formed in theunderside of the barrel 42 for engaging a notch 60 in the forward end.of the plunger. posed between a rear extension 62 of the trigger and thebarrel for holding the finger in raised position. The trigger '55further includes a downward extension 63 to which there is con nected apull rod 64 which passes through a bore 65 formed in the body member,the rod 64 terminating in a finger-engaging lug 66, exteriorly of thebody. A guard 61 surrounds the lug 66 so as to prevent accidentalrelease of the trigger.

A carriage 68 is provided for support of the model airplane 33 and isoperatively connected to the plunger 48 (see Figures 2', 5 and 6).

al strip 'fl as at 1 2. The stripj'II isformedwith A small coiled springBI is inter- The carriage includes a frame 69 which embodies a in thebelly of the plane.

- so that the arm 9!. will be movedinadownW-Idf direction so as towithdraw the hook.frorn,.tl'i 'ef' a series of apertures 13 which areadapted to register with suitable apertures formed in a pair of opposedguide members I4 and 14', bolts 15 being extended through alignedapertures and engaged by suitable nuts for maintaining the uides uponthe strip 1 I. The guide members I4 and 14 are adapted to engage thelower front portion of the airplane 33 and are adjustable towards oraway from each other to accommodate planes of various sizes.

The bars I0 and I0 are additionally braced by strips I6 and I6 extendedtransversely thereacross and secured by bolts 11. Upon the bars 10 andI0 there is secured a sub-frame 18 of rectangular form consisting ofparallel side stringers 19 connected by transverse straps 89, 8 I, and82. In advance of the strap 88, a shaft 83 is journalled in thestringers 19 and has a sleeve 84 mounted thereon. A transverse thrustpin 85 extends through the sleeve 84 and is fixed thereto. A stop member86 disposed beneath the sleeve 84 and secured between the stringers "I9is provided. This stop serves to limit r'otative movements of the sleeve84 by engagement with the pin 85. I The pin 85 is of a lengthto'project' into a cell or compartment 81 formed in the bot: tom ofairplane 33, (see Figure 3) so that as the plunger 48 moves towards thefront in the bar rel 42, the airplane will likewise move therewith.

In order that the carriage 69 and airplane 33 may move in unison alongthe barrel, the. ca r'I- 'v riage 69 is provided with a pair ordepending parallel sidewalls 88, which are each provided with spacedopenings 89 in" registry with the trunnions 49 of the plunger 48 andsecured by means of bolts or screws 99; asbest seen i!'1fl-" lg-'- ure 2of the drawings.

A means is provided for releasing the plane 33 from the carriage inorder that the plane may. assume its flight and this means comprises'anarm 9| which is pivotally mounted on a pin 92 secured in parallel spacedstringers 98 connected' between the straps BI and 82. The arm 9 I,isformed at its forward end with a hook member 94 adapted to project intoan opening 95 formed The arm 9| has a downwardly projecting trip 98 anda rear extension 9'1, the latter being engaged by a spring '99 supportedupon the strap 82, the spring holding the hook 94 in raised positionwithin the open ings 95 of the plane. As long, as' the hook 9411sengaged with the opening 95, th'eplane cannot leave the carriage, andfor releasing the hook 94, of the arm from the plane a lug 99projects'upwardly from the barrel in thepath of thef fii l-96v opening95.0f the airplane, theflairplanejthuslbeing released from the,carriage. Eor'fmaintaining' thev hook portion 94 olitfof, the o ening95; a flat leaf spring IOIIIhas. one/end secured ,to one of thestringers 93fb'y screws I|l (see; Figure 5)- and carried by theothe'rend .ofthe spring I99,

there is a'transverse pin I82.which is forcedthrough a slot Ifl3 inthe'strin'ger Blasfsoonas the arm'SI is moved below the slot I03(Figure;8 )f

The pin I82 maintains ..the,arm 9| .inits down ward position untilth'enext plane. launehed, when the operator merely retracts the pin I92 soas to clear the arm 9|, the spring98 returning.

the arm to .its raised position in advance. of .the

pin I02, the latter 'being held under, tension by theleaf spring I99.

'From the structure thus far described;

e eeg l ei.Warmers. preeminence supported, but iobviously,athe rear ofthe plane must also besupported by'the carriage-69 ,-and as may be seenin Figures .5 and 6, the rear ends of the frames 10 and 10. terminate inrespective quadrants I04 each of which hasan ,arcuate. slot I formedtherein.

A shaft I08 extended transversely between the 2 frames -10 mountsasupport member I01 as will now be described. The member I01 com- 1prises a pair of leg members I08 converging toward the longitudinal axisof the carriage 69 where the legs are joined with a sleeve I09. The

which a sleeve II3 is suitably secured, the sleeve II3 being inalignment with the sleeve I89, A

threaded shaft I I4 is extended through the sleevesI03 and H3 and locknuts Ii5 complemental to respective ends of the sleeves function tosecure the shaft in an adjusted position. 0b-

viously byjloosening the nuts II5 the shaft may 7 be moved inwardly oroutwardly with respect to the sleeves for obtaining an adjustment as tolength of the support member I01. Upon the rear end of the rod I I4there is threadedly engaged a sleeve I I8 which is secured thereon by alock nut H1. The sleeve II5 has itsouter end flattened as best seen inFigure 7, for reception of spaced legs II8 of an upwardly opening yokeH9. The legs II8 of the yoke are apertured, as is the flattened end ofthe sleeve I I6 and through these apertures there is engaged a wing boltI for securing the yoke H9 in adjusted positions for support of rearportions of airplanes.

A manually operable means is .employed for retracting the plunger48 andits associated carriage 89, and as best seen in Figures 8 and 9,.

this comprises a housing I2I fixed, tothe rear end of the barrel 42, thehousing having a partition.

I22 and an outer closure plate I23, and between the partition andclosure plate, a shaft I24 is suitably journalled, extendinglongitudinally of the barrel 42. keyed to the shaft I24 and about thedrum I25 there is wound a cable" I21, trained through a guidepulley I28mounted exteriorly of the housing IZI in a suitable bracket I29. The endof the cable I21 has a hook I30 for engaging a ring I3I secured in anopening I32 of the next adjacent plate 88 of the carriage B9. A similarcable I33 is wound upon the drum I26, trained around a pulley I34, theterminal end of the cable I33 having a hook I35 for engagement with aring I38 fixed in an opening formed in the next adjacent plate 88 of thecarrier.

The shaft I24 is rotated by means of a hand crank I31 and the cables I21and I33 are so wound upon their respective drums I25 and I26 as tosimultaneously move in the same direction. In order to prevent thespring 53 from forcing the plunger 48 forwardly during the retractingmovement of the carriage, a ratchet wheel I38 is keyed to the inner endof the shaft I24, there being a pawl I39 cooperable with the teeth ofthe ratchet wheel.

In order to support the landing wheels I40 of the airplane 33 respectiverunways I4I are disposed and suitably mounted at respective sides of thecatapult M, which as here shown, are

A pair of drums I25 and I25 are supported upon upright rods I42telescopically The rods I42 are secured in vertical adjusted positionsby means'of wing bolts. I44; The sockets I43 are .mounted' uponrespective sleeves I45 horizonmounted in vertical sockets I 43.

tally slidable on the rods I9. The sleeves I45 are securedlinan'adjusted position by means of wing bolts I48. On intermediateportions of the runways I4I are supported sleeves I 45 which .areadjustably mounted upon the rods 23, there Z being adjustable uprightrods I42 in each-of the sockets (see Figure 10).

A modified form of runway is illustrated in Figure 11, wherein therunway I41 is formed with longitudinally spaced openings I48 in each ofwhich there is revolubly journalled a roller I 49. This. construction ofrunway is admirably suited for support of pontoons of amphibious planes.

In Figure 12, there is shown a construction of support for the catapultwherein the standards I0 at the front and rear of the structure areadjustable with respect to the vertical so that the standards I0 may bepositioned at an angle to a supporting surface and thus afford As hasbeen greater rigidity to the structure. explained the standards I0 areswivelly mounted to the rods I4, by virtue of the T-fittings I3.

A brace bar; 20' is extended between the stand ards I0 at the front andrear, at respective sides the bar 20 being vivotally connected on a pin20" of one of the standards I0. standard I0 has a pin 20a complementalto a longitudinal slot 20b formed in the brace bar 20'. Suitable wingnuts 200 are engaged upon the pins 20" and 20a, for securing theadjustment of the legs of the standards. Also, by

this construction, it will be apparent that the I brace bar 20 may bereleased from the legs to permit folding of the legs for readytranspor-.

tation of the catapult.

In .Figure 13 a modified form of support for. the catapult is shown, thesupport being in the.

form of a firearm embodying a shoulder. stock I50, a'main body or barrelstock I5I,'. the underefiecting launchingof a plane. justable rods I53 1are suitably supported in brackets I54 spaced at proper positions alongthe stock and barrel for support of the rods 3I.

The operation of the device is as follows:

Assume that the airplane 33 is in the retracted position shown in Figure3. The airplane is of course a conventional model airplane and isprovided with a suitable engine or gasoline motor (not shown) forpropelling or driving the airplane 33 after the airplane has beenlaunched by the catapult of the presentinvention. Then, the user insertsone of his fingers into engagement with the lug 68 and moves the pullrod 64 rearwardly to the position shown in Figure 4. At the same timethe pawl I39 is manually moved out of engagement with the ratchet andthe movement of the pull rod 64 causes the trigger 55 to pivot about thepin 51 so that the finger 58 is moved out of engagement with the notch60 in the lower front end of the plunger 48. Thus, the spring 53 thrustsor forces the plunger 48 forwardly, and it carries the carriage 68therewith, since the pins 49 project from the plunger 48 and intoengagement with the openings 88 of the side plates 88. It will be notedthat the thrust member projects into the cell The other Figure 3.Therefore, when the carriage; moves forwardly the'airplane 33 is-alsothrust forwardlybymeans of the. member 85;. Further,,the:.hool:,

portion. 94.: of the arm 9,1 is. arranged in: en,- gagement. with. therecess; 95; so that :.the.= airplane cannot, disengage. itself-zf'rom,the carriage when the-carriage. and airplane are in. their, retractedrunwayse, said upright; supports: being; verticallm and laterallyadjustable with respect to; said: transverseibar; members, azrailimemberconnected to the' uppen endszoi said upright supports-iand. extending,parallel with said runways for. engagfing and supportingrespectivewings' of thereinplane;

2'. A catapult for launching amodel airplane comprising a. supportingstructure having trans Position-a HOW-ever; after the Piston mlvesi l0.verse b'armembers, a-pairof runways supported forwardly a smalldistance, the lug or. trip:'9,9

contacts the lower end.96,of;the, arm 9l to theretbarrel; the shockabsorber 16556115 or reduces;

on saidtransver'se bars, said runways being vertically andlaterallyadjustable to accommodate: landing wheels of various types ofairplanes, up rightsupports carried by said transverse bars 15 disposedat opposite sides 'of said runways; saidthe, jarring or impact causedbythe, forwardly moving; piston. Now, the airplane 33 hasr'been' given asufiicient; forwardly moving; impetus: s0 thatrthe airplane lisp-nowable toflyawaymnder;

its-own power. To launch-additional airplanes, the; user merely rotatesthecrank or. handle 1 I37, to thereby wind-the, cable; o1 1to,the;nulley s; I25;

and I2-6so that the: piston, 48 is moved-xfromthe, position showninuFigure etothe; position. shown in-Figure:3;and the finger;58 of thetrigger;

55,-: again; maintains the plunger; 18v in; its re-. tracted position.

Asathe airplane advances; alon ;v the, catapult;

the, wheels I 40 ride-in the tracks I iofthe device;

andthe wings 32 of the airplane are slidably:

1; A1catapult for. launchinga modelairplane;

comprising a supporting structure having trans-.-

verse bar. members, a;pairotrunwayssupported onvertically adjustableuprights said uprightsi being laterally: adjustable on,said'vtransver'se bars r to accommodate landingwheels of various :types,5

ofgairplanes; upright 1 supports: carried .by said: transversebarsgdisposedat opposite sides :of;,said;

uprlght supports being vertically and'laterallya'd justablewitli'respect to said'transverse bar mem--- bers, a rairmember' connected 'tothe upper 'ends off'said upright supports and extending parallelwithnsaid runways'for engaging and supporting respective Wingsofthe'aii'plane; a carriage sup-- ported by said supportingstructure-disposed between said runways-and longitudinally movable alongsaid supporting-structure; means releasably" connecting an airplane tosaid carriage, means for forcibly moving the carriage and airplanetoeffectmovement of theairplane along'said run-- ways; and automaticmeans for actuating the re-- leasing means between the carriage andairplane:

NORMAN D; ASHWODU REFERENCES CITED" The following references are 'of'record in the file of thispatent:

UNITED STATES PATENTS Number Name Date 1,832,740 Ripplet a1 Nov.17,'1931 1,846,157 Stevens Feces; 1932 2,070,721. Feight Feb. 16, 19372,144,805 Koch etal 'Jan; 24, 1939 2,204,546 Fleet et al.' June'l8, 19402,330,739 Olaszy: Sept. 28, 1943 2,406,131 Branham' Aug; 20, 19462,425,886 Knox Aug. 19, 1947 2,426,437 Cole et a1 Aug; 26; 1947 FOREIGNPATENTS Number Country; Date 9,403 Great'Britain" -1912 835,594,. France.Sept. .26, 1938:

